CA2731756C

CA2731756C - Method for repairing and/or upgrading a component, especially of a gas turbine

Info

Publication number: CA2731756C
Application number: CA2731756A
Authority: CA
Inventors: Alexander Stankowski; Lukas Emanuel Rickenbacher; Simone Hovel
Original assignee: Alstom Technology AG
Current assignee: Ansaldo Energia IP UK Ltd
Priority date: 2010-02-22
Filing date: 2011-02-14
Publication date: 2016-04-05
Anticipated expiration: 2031-02-14
Also published as: EP2361720A1; CA2731756A1; US20110264413A1; EP2361720B1

Abstract

The invention refers to a method for repairing and/or upgrading a component (10'), preferably of a gas turbine, especially a blade (10'), which component has been deformed during operation. A simplification with cost advantages is achieved by a first nominal CAD model (M1) of the non-deformed component (10) being made available, by the deformed component (10') being measured, by the first CAD-model (M1), with the aid of the data determined on the deformed component (10'), being transformed into a second CAD model (M2) of the deformed component (10') by morphing, by a cutting line, which determines a cut-out in the component (10'), and also an insert piece, which can be inserted in the cut-out, being established in the second CAD model (M2), by a cut-out being introduced into the component (10') in accordance with the cutting line, by an insert piece for inserting in the cut-out being manufactured in accordance with the cutting line, by the manufactured insert piece being inserted in the cut-out, and by the inserted insert piece being connected to the component (10') in a materially bonding manner.

Description

DESCRIPTION
METHOD FOR REPAIRING AND/OR UPGRADING A COMPONENT, TECHNICAL FIELD
20 The present invention relates to the field of machining finished components, which are built in a modular manner or are monolithic or hybrid components. It refers to a method for repairing and/or upgrading such a component, especially of a gas turbine.
BACKGROUND OF THE INVENTION
Gas turbines, for reasons of good efficiency, today have operating temperatures in the hot gas range of over 1400 C. It is therefore not surprising that a large number of components of gas turbines, such as rotor blades, stator blades or combustor liners, are exposed to large thermal and also mechanical loads.
Since these components are customarily produced from expensive high-temperature

2 materials, it is desirable to repair them instead of completely replacing them if they are damaged. Furthermore, there is frequently the need to upgrade already installed components in order to enhance them in their functioning mode or to adapt them to changing operating conditions.
A method for replacing parts of turbine blades is known from printed publication US 5,269,057. In the case of this known method, a region of the blade, which is to be replaced is identified and then removed by means of a non-conventional machining process. In the same way, a replacement piece is produced, provision being made for engagement elements with which the replacement piece is mounted in a form-fitting manner on the blade. The parts are then interconnected in a materially bonding manner. For cutting out the region, which is to be replaced, and the replacement piece, one and the same CNC program is used for operating a spark-erosion machine.
A method for repairing and/or modifying components of a gas turbine is disclosed in printed publication EP 1 620 225 B1 , in which first of all at least one section of the component which is to be repaired or to be modified is machined out of the component, especially cut out. A data set is then created for a replacement part, which is to be produced, at least in the case of the initial repair or modification of this section of the component. The replacement part is subsequently produced by means of a rapid manufacturing process.
After, or even before, the machining out, especially cutting out, of the particularly damaged section and also, if applicable, of a tolerance section adjoining the damaged section, from the component which is to be repaired, a data set is created for the replacement part which is to be produced. In this context, a three-dimensional CAD data set is first of all created for the replacement part, which is to be produced. This 3D-CAD data set for the part, which is to be replaced is then transformed into a machine data set. First of all, a check is carried out as to whether a 3D-CAD data set exists for the component, which is to be repaired or the component which is to be modified, but undamaged, or for a corresponding

3 new part. If such a 3D-CAD data set exists for the undamaged component, then a check is then carried out as to whether firstly there is systematic damage of the component and whether secondly the geometry of the damaged component can be reproduced. In the case in which both a systematic damage of the component exists and at the same time the geometry of the damaged component can be reproduced, based on static evaluations of the extent of the damaged section of the component which is to be repaired and also taking into consideration a tolerance section adjoining the damaged section, the previously damaged material regions, and also highly stressed regions of the component during the repair considered, the required geometry of the replacement part which is to be produced can be derived and from it the 3D-CAD data set can be generated.
If, however, no systematic damage of the component, which is to be repaired exists and/or the geometry of the component which is damaged or is to be modified cannot be reproduced, then reverse engineering of the component, or at least of the relevant component regions, is carried out. For carrying out the reverse engineering of the component or component region, first of all the particularly damaged section and also, if applicable, additionally the tolerance section adjoining the damaged section, are machined out of the damaged component which is to be repaired. A measurement of the component or component region is then carried out, for example by means of mechanical or optical measuring sensors or by means of computer tomography and subsequent surface feedback. As a result, a 3D-CAD data set of the component, or component region, which is damaged or is to be modified, from which the damaged section and, if applicable, a tolerance section, have been previously machined out, is obtained. From this 3D-CAD data set of the machined component or component region, the 3D-CAD data set of the replacement part, which is to be produced is determined by forming a difference with the 3D-CAD data set of the undamaged component.
Such a reverse engineering, however, is altogether very costly.

4 SUMMARY OF THE INVENTION
An aspect of the present disclosure is to develop a method of the type referred to in the introduction so that the disadvantages of the previously known methods may be avoided and a repair or upgrading of the component can be carried out in a particularly simple and inexpensive manner.
According to an aspect of the present invention, there is provided a method for repairing or upgrading a component, which has been deformed during operation, the method comprising making available a first nominal CAD model of the non-deformed component; measuring the deformed component, transforming, with the aid of data determined on the deformed component, the first CAD model into a second CAD
model of the deformed component by morph ing, establishing in the second CAD
model a cutting line, which determines a cut-out in the component, and also an insert piece, which can be inserted in the cut-out; introducing into the component the cut-out in accordance with the cutting line; manufacturing an insert piece for inserting in the cut-out in accordance with the cutting line; inserting the manufactured insert piece in the cut-out, and connecting the inserted insert piece to the component in a materially bonding manner.
In some embodiments, the component has damage and/or a region, which is intended for an upgrade, and the damage or the region intended for the upgrade is removed from the component by introducing the cut-out into the component.
In some embodiments, the deformed component is measured in its entirety by means of a non-destructive method.
In particular, in some embodiments, the deformed component is mechanically and/or optically scanned in a three-dimensional, external scanning process.
In some embodiments, the internal structure of the deformed component is preferably also non-destructively scanned, especially by CT methods or ultrasonic methods, or determined on the basis of a few reference points, wherein in addition to the deformation of the external contour of the component the second CAD model also takes into consideration deformations of the internal structure of the component and also deformations of possible cooling holes.
In some embodiments, the second CAD model additionally also takes into

5 consideration changes as a result of material loss, especially changes in the thickness of walls in the component.
In further development of the method of some embodiments, the cut-out is introduced into the component by means of a mechanical machining process, especially by means of Electrical Discharge Machining (EDM).
According to another development, the insert piece has a geometry, which deviates from the geometry of the part, which is removed from the cut-out.
In a further development, all associated internal and external deformations of the component are included in the geometry of the insert piece.
In some embodiments, a CAD model is generated for the manufacture of the insert piece on the basis of the cutting line, and the insert piece is manufactured in accordance with the generated CAD model, especially by means of casting, additive manufacturing processes or a mechanical machining process, such as milling or electrochemical machining.
In another embodiment, the insert piece is manufactured oversized at prespecified points, and the insert piece is subjected to aftermachining after manufacture.
In some embodiments, the inserted insert piece is connected to the component in a materially bonding manner by means of automatic or manual welding.
In some embodiments, the inserted insert piece is connected to the component in a materially bonding manner by means of high-temperature soldering.

6 In some embodiments, the component is aftermachined with regard to the external contour after the insertion and materially-bonding connection of the insert piece.
BRIEF EXPLANATION OF THE FIGURES
The invention shall subsequently be explained in more detail based on exemplary embodiments in conjunction with the drawings. In the drawings Figs. 1-7 show different steps in the method for repairing and/or upgrading a component of a gas turbine according to an exemplary embodiment of the invention, wherein a new component (Fig. 2) is produced according to a nominal first CAD model (Fig. 1), while a damaged and deformed component from a gas turbine (Fig. 3) is measured (Fig. 4), an associated second CAD model with the measured data is developed from the nominal CAD model by morphing (Fig. 5), a cut-out in the component and a matching insert piece are defined on the basis of this second CAD model (Fig. 6), and finally a manufactured insert piece is inserted in the machined-out cut-out (Fig. 7).

7 DESCRIPTION OF EMBODIMENTS
The invention is exemplarily explained in the following text based on a blade of a gas turbine. In Fig. 2, in a greatly simplified form, a blade 10 for a gas turbine is shown, having a blade root 11, a platform 12 and a blade airfoil 13 in a known per se manner. The blade airfoil 13 has a leading edge 15 and a trailing edge 14 and terminates at the top in a blade tip 16. In the example, which is shown, cooling holes 17, through which cooling air, which is introduced inside the blade airfoil 13 can discharge, are arranged in the region of the leading edge 15. The blade 10 of Fig. 2 is produced according to a nominal first CAD model which is schematically reproduced in Fig. 1 with dash-dot lines and with the designation Ml.
If the blade 10 which is produced according to the CAD model M1 has been in use in its operating position in a gas turbine for a considerable time, it may have not only damage but may also be deformed on account of thermal and mechanical stress during operation. The new blade 10 then changes into a damaged and deformed blade 10' which is shown in Fig. 3 with its deviation from the original shape. Exemplary damage 18 in the form of a crack is located in this case in the region of the trailing edge of the blade 10'.
After removal from the gas turbine, the deformed and damaged blade 10' is measured according to Fig. 4. This is carried out by means of a non-destructive method. A mechanical scanning device 19 with a scanning probe tip, with which the external contour of the deformed blade 10' is traced, is shown as an example in Fig. 4. An associated evaluation unit 20 evaluates the measurement results.

For this three-dimensional scanning process, a suitable optical scanning device can naturally also be used instead of the mechanical scanning device 19. With the aid of the measurement results of the scanning process, a second CAD model M2, which corresponds to the deformed blade 10', is generated from the nominal CAD
model M1 by means of so-called morphing (see Fig. 5).

8 The newly generated CAD model M2 includes deformations of the external contour, of the internal structures and of the cooling holes 17 on the basis of the previously determined scanning data. Material loss on the internal contour or the influence of a displacement of the blade core can be determined by means of non-destructive measuring methods, such as computer tomography (CT) or ultrasonic measuring, or based on a few reference points. Data from such measurements can also be recorded in the newly generated CAD model M2 of the deformed blade 10'.
In the newly generated CAD model M2, a predetermined, freely selectable cutting line (21 in Fig. 6) can now be drawn in in order to generate a CAD model of the geometry of a corresponding insert piece (23 in Fig. 7) which is to be produced.
With this cutting line 21, the cut-out 22 (Fig. 7), which ensues as a result of removing the damaged region of the blade 10', is established at the same time.
In this case, no provision needs to be made for an additional oversize for the insert piece 23 in order to compensate a material loss during mechanical machining out of the cut-out 22. The cutting line ¨ like in the case of the above-cited US
5,269,057 - may be complex and in particular formed so that a form-fitting connection between blade 10' and insert piece 23 results.
The machining out of the cut-out 22 is preferably carried out by means of a mechanical machining process, such as spark erosion (EDM). The geometry of the region of the blade 10' which is removed in the process does not need to be retained because it does not have to be scanned and is not required for generating a CAD model for the insert piece 23. Because the geometry is not required, even very complex cutting lines 21 can be selected.
The geometry of the insert piece 23 takes into consideration all information, which refers to deformation (external and internal contour, internal cooling structure, etc.) In each case, no reverse-engineering step is necessary in order to generate the CAD model for the insert piece 23. Nevertheless, the geometry of the insert piece 23 can be modified by means of CAD modeling in the case of special damage, or

9 in order to be able to fulfill special requirements (design upgrade, new cooling structure, etc.) The insert piece 23 is manufactured according to the generated drawings. This can be carried out by casting, additive manufacturing processes, or by a mechanical machining process, such as milling, or by electrochemical machining.
An additive manufacturing process, for example selective laser melting, is preferably used.
The geometry or geometric details of the insert piece 23 (for example cooling ribs on the internal contour or cooling holes) can also be created within the scope of additional aftermachining. As a result of this, geometric structures or details can be realized which otherwise would not be able to be realized within the scope of the production process (for example additive manufacturing processes, such as rapid manufacturing). For this aftermachining, provision has to be made at the corresponding points for additional material or for an oversize.
According to Fig. 7, the manufactured insert piece 23 is then inserted in the corresponding cut-out 22 in the component 10' and connected to the component

10' in a materially bonding manner. For this, manual or automatic welding or high-temperature soldering can be used. Finally, after the connecting process, a recontouring can be carried out in order to achieve an even or modified contour of the repaired component.
The method according to some embodiments may include characteristic features and advantages from among the following:
= The complete information of the nominal first CAD model is included in the second CAD model of the deformed component (external contour and internal cooling structure).
= The drawing for the insert piece or replacement piece is derived from the second CAD model of the deformed component; for this, only the establishing of a cutting line is required, but not reverse engineering.

= Changes in the internal and external contours, of the internal cooling structure and also changes in the wall thickness, are included in the CAD
data set.
= The method can be carried out within the scope of conventional CAD
5 software. Special software or interfaces are not required.
= The generation of the CAD data and of the CAD model for the insert piece requires only a small outlay.
= In general, no reverse engineering is required.
= A comparison between the overall nominal geometry and the current 10 geometry of the component is not necessary. A limitation to the part of the component in which the repair or the upgrade is to be carried out is sufficient.
= The geometry of the removed component region does not have to be stored since scanning of this region for generating the drawing or generating a corresponding data set is not necessary. Since for this reason the component region does not have to be removed in one piece, different methods can be used for the removal.
= For the same reason, more complex cutting lines can be used and increased flexibility in the process can be achieved.
= On account of the high accuracy of the method, the insert piece, which is produced by means of additive manufacturing processes or mechanical (cutting) machining, requires no individual adjustment and no aftermachining, or only very little aftermachining.
= Casting processes have large manufacturing tolerances. Therefore, cast insert pieces require an adaptive machining step if a close gap tolerance is required during the materially bonding connecting process. In the case of manual welding, such an adaptive machining step is not required, but is of necessity in the case of high-temperature soldering on account of the creation of the capillary effect for the solder.
= The proposed solution is flexible and inexpensive so that it can be used for the definition and optimization of the cutting line, of the connecting method and of fixing of the insert pieces. The geometry of the cutting line can be

11 easily modified in the case of newly generated CAD data. Complex cutting lines, which are not restricted by any machining process, can also be modeled for trials. With an additive manufacturing process, slightly different geometries can be created for trials (both a section of the component with the cut-out as well as the insert piece). Trials with different cutting lines as well as with different connecting methods can be conducted, and the mechanical characteristics, such as LCF (low cycle fatigue), TMF (thermo-mechanical fatigue) and behavior under stress of long duration, can subsequently be tested, for example by means of thermoshock tests, tensile test, etc.
Naturally, the invention is not limited to the described exemplary embodiment.

It is applicable both to components of any type, which are built in a modular manner, and also to monolithic, and hybrid components.

12 LIST OF DESIGNATIONS
10, 10' Component, for example blade of a gas turbine 11 Blade root 12 Platform

13 Blade airfoil

14 Trailing edge Leading edge 16 Blade tip 10 17 Cooling hole 18 Damage 19 Scanning device (mechanical and/or optical) Evaluation unit 21 Cutting line

15 22 Cut-out 23 Insert piece M1, M2 CAD model

Claims

CLAIMS:

1. A method for repairing or upgrading a component, which has been deformed during operation, the method comprising: making available a first nominal CAD model of the non-deformed component; measuring the deformed component;
transforming, with the aid of data determined on the deformed component, the first CAD model into a second CAD model of the deformed component by morphing;
establishing in the second CAD model a cutting line which determines a cut-out in the component, and also an insert piece, which can be inserted in the cut-out;
introducing into the component the cut-out in accordance with the cutting line;
manufacturing an insert piece for inserting in the cut-out in accordance with the cutting line;
inserting the manufactured insert piece in the cut-out, and connecting the inserted insert piece to the component in a materially bonding manner.

2. The method as claimed in claim 1, wherein the component has one of or both damage and a region which is intended for an upgrade, and comprising removing the damage or the region which is intended for the upgrade from the component by introducing a cut-out into the component.

3. The method as claimed in claim 1 or 2, comprising measuring the deformed component in its entirety, or based on a few reference points, by means of a non-destructive method.

4. The method as claimed in claim 3, comprising one of or both mechanically scanning and optically scanning the deformed component in a three-dimensional, external scanning process.

5. The method as claimed in claim 4, further comprising non-destructively scanning the internal structure of the deformed component and, in addition to the deformation of an external contour of the component, the second CAD model also takes into consideration deformations of the internal structure of the component and also deformations of possible cooling holes.

6. The method as claimed in claim 5, wherein said non-destructive scanning is performed by a CT method or an ultrasonic method.

7. The method as claimed in claim 4, further comprising determining the internal structure of the deformed component on the basis of a few reference points and, in addition to the deformation of an external contour of the component, the second CAD model also takes into consideration deformations of the internal structure of the component and also deformations of possible cooling holes.

8. The method as claimed in any one of claims 5, 6 or 7, wherein the second CAD model additionally takes into consideration changes as a result of material loss.

9. The method as claimed in claim 8, wherein the changes taken into consideration by the second CAD model include changes in the thickness of walls in the component.

10. The method as claimed in any one of claims 1 to 9, wherein the cut-out is introduced into the component by means of a mechanical machining process.

11. The method as claimed in claim 10, wherein the mechanical machining process comprises Electrical Discharge Machining (EDM).

12. The method as claimed in any one of claims 1 to 11, wherein the insert piece has a geometry, which deviates from the geometry of the part, which is removed from the cut-out.

13. The method as claimed in any one of claims 1 to 12, wherein all associated internal and external deformations of the component are included in the geometry of the insert piece.

14. The method as claimed in any one of claims 1 to 13, further comprising generating a CAD model for the manufacture of the insert piece on the basis of the cutting line, and manufacturing the insert piece in accordance with the generated CAD model.

15. The method as claimed in claim 14, wherein the insert piece is manufactured by means of casting, or an additive manufacturing process or a mechanical machining process.

16. The method as claimed in claim 15, wherein the mechanical machining process is milling or electrochemical machining.

17. The method as claimed in any one of claims 1 to 16, wherein the insert piece is manufactured oversized at prespecified points, and the insert piece is subjected to aftermachining after manufacture.

18. The method as claimed in any one of claims 1 to 17, wherein the inserted insert piece is connected to the component in a materially bonding manner by means of automatic or manual welding.

19. The method as claimed in any one of claims 1 to 17, wherein the inserted insert piece is connected to the component in a materially bonding manner by means of high-temperature soldering.

20. The method as claimed in any one of claims 1 to 19, comprising after machining the component with regard to the external contour after the insertion and materially-bonding connection of the insert piece.

21. The method as claimed in any one of claims 1 to 20, wherein the component is a component of a gas turbine.

22. The method as claimed in claim 21, wherein the component is a blade.